CA2148797A1

CA2148797A1 - Combined flying machine

Info

Publication number: CA2148797A1
Application number: CA002148797A
Authority: CA
Inventors: Viktor Mikhailovich Kapin; Valery Andreevich Ivchin; Nikolai Serafimovich Pavlenko; Evgeny Lvovich Pogrebinsky; Viktor Vladimirovich Subbotin; Oleg Nikolaevich Maiorov
Original assignee: Individual
Current assignee: TOVARISCHESTVO S OGRANICHENNOI OTVETSTVENNOSTJU KOMPANIA "INALET"
Priority date: 1993-09-07
Filing date: 1994-09-02
Publication date: 1995-03-16
Also published as: EP0667283A1; DE59405105D1; JPH08503672A; NZ273413A; PL309029A1; EP0667283A4; WO1995007215A1; FI952208A0; NO951788D0; US5873545A; RU2012512C1; CZ121395A3; ES2113676T3; AU679564B2; NO951788L; FI952208A; EP0667283B1; AU7668294A

Abstract

COMBINED FLYING MACHINE A combined flying machine comprises a fuselage (1) in the dorm of a central thick wing with a vertical open tunnel (2), in which there is mounted a lifting rotor (4). Said machine is also provided with outboard wings and a tail unit (8). The machine is equipped with a landing device on an air cushion (19) that surrounds an outlet from the tunnel. A power plant of said flying machine comprises two engine modules (13), disposed from two sides of the tunnel (2) and collected with the lifting rotor (4) and the propulsion propellers (12). The area of the tunnel cross-section in the plane of the lifting rotor rotation amounts to 0.3 to 0.8 of the area of the landing device air cushion, which ensures a safe landing of the flying machine on an unprepared landing site even with a failure of one of the engine modules.

Description

7 9 7 ~

COM~INED F~YING ~ACHINE 3 ., ~
~ield of the Inventi.on . ~5 T~e pre~ent lnvention rel~tes to the aircr~ft produc- ~ :
tion ~nd can be utilized in ~Tyin~ m&chine3 with vertio~
S take-of~ and l~nding of YarioUs ~fl~i~nments ~ pa~enger-c~rrying, cargo, car~o-pa~en~er, ~mbul~nce ~nd other ~pe- , ci~l purpoee Qircr~Lft.

~rior Art . .
lylng maohines with ~ertlc~l t~ke-o~f ~nd l~ndin~
10 belong to promi~ing directions in t~e development o~ the ~vi~tion msteri~ they c~n be employed on unprepared.
l~ndlng ground~. Such m~chine3 are e~peolally ~ppe~lin~
~or ~pecisl-purpese ~viation and local-~ervice ~lr routes.
2here are 3everal types of flyin~ ~chines with vertical . .
15 take-of~ ~nd l~ndlne.
There ~re known ~lyl~ machine~ wlth ~ertic~l t~ke-o~f and lBndi~ in which the lirt force durln~ the take-o~f ~d l~ndin~ is induced thanks to the reaetiv~ forco `
of a high-~elocity ~et. For instnnce, the flying m~chlne, 20 ~et *orth in the ~RD patent No. 1246422, Cl. B ~0 ~ 3/08 t~2a~ 62b-60) o~ 1967~ comprlse~ 8 cylindric~l fu~elage :~
with winga Bnd ~ tail unit, power pl~nt~ for the level ~l~ght, dl~po~ed under the wing, Qnd power pl~nt8 for ta-ke-off and landi~. Sal~ ~ower plsnts ~or take-o~f ~nd l~ndlng ~re hrranged in glo~e~ of the middle par~ of the fuaela~e. A dr~wbaok of thi8 type o~ the arran~ement i3 hleh fuel con~umption under the t~ke-off ~nd landing con-dltions and B complic~ted design of ~aid m~ohine, 8~ nce it i8 neces~ary to h~ve ~dditional engi~es in th~ pow~r . .
30 plent~ for vsrtical take-o~i and l~ndi~g. ~urthermore, ~aid hieh-veloc~ty ~et during take-of~ ~nd landin~ h~ a profound imp~ct on the ~urf~ce o~ the landing ground, whlc~ make~ the operat~o~ of the machines o~ thls type im-poe~ible from Aoll ~ite~. ::
' In the p~iox art there i~ known a ily~ng m~chine with : ' ',. ''~', , 7 9 ~ ~

vartic~l taks-off ~nd l~nding that con~titute~ a combl~a- ~ .
tion of ~n ~irpl~ne ~nd a helioopter, descrlbed i~ the USA p~tent.No. Re 29023, C1. 244-6 of 1976. S~ld flyi~
mAChlne i8 proYided with ~ fu~el~ge h~vin~ a high-mounted 5 wing ~nd verticsl fin~ ~t the wing tips. The w~n~ i~ mRnu- ~ :
~ctured with a s~miolrcul~r cut-out of the trailing edge.
Over the ~te~n part of the ~uselage there i~ mounted ~ lif- , -ting ro~or, the pl~e of rot~tlo~ of wh~ch coincldes with the ~orizontal pl~ne of the wing- ~he flying m~chine ~ 9 , ~ : :
equipped al~o with power planta for the level ~light. .
The pre~ence of an open liftiLg rotor e~enti~lly .
imp~ir~ the aerodyn~mic~ oi ~ld machine in the level crui~in~ fllght. Furthermore, the o~er~ll dimen~ion~ of ssid li~ting rotor ~nd its tr~nsmis~ion system ~re ~uch th~t ~Bid lifting rotor wlll alw~y~ be over the ~u.sel~ge or ~ny ~ther ~upporting structure, which ~dversely ~f~eots the characteristic~ of the flying m~chlne ~t the t~ke-o~f snd l~nding due to ~he trsn~ver~e flow over the ~us~lage.
There are known in the pxior urt combinsd ~lyin~ .
m~¢hinea in which li~t during take-off ~nd l~ng ~nd thru~t ef~ort in the ~e~el fllght are de~sloped by ~ - .
le de~ice - tilt propeller. Suoh ~ flylng machine is des-cribed in tho Gree,t ~ri~in p~tent No. ~405737, Cl~ B 7 W
of 1975. Sa~d prior ~rt ~lying m~chine comprise~ ~ ~u~e- ~ :
25 la~ with wings snd a tail unit. Said win~s ~re m~de up ::
til~ing, snd power pl~nts along wit~ prop~ller~ ~re mount- - -ed on ~ha tiltable part o~ the wing~ . The ~me propeller~
~re.employed ~or de~elopine ~ ll~t force for take-off ~nd landi~g as well Bg ~or gen0r~ting ~ thru~t ~or the le~el 30 flight. ~he ~rr~n~ement with ~ld tilting wlng diepl~y~ -~
~d~ntages ~n comp~rlson with the open lifting motor, worked up by a lot of de~ign~r~ and embodied in real m~chi- ~ ~
n~s. The us~ o~ one ~nd the s~ma propeller for ~ertic~l :
ta~e-of~ ~nd l~nding and for the level flight, ho~ever, 35 imposes very strict requirement~ to said propeller. The ; : .-tiltin~ propcller msy not fe~ture the sMme dicmeter as the llftin~ rotor o~ the helicopter, and therefore the ~peci~

~ ~148797 _ 3 _ fic load on ~aid propeller duxing the tako-off and l~nd-ing i~ greater th~n that of the helicopte~. Aa a c4nsequ-ence, a gre~t~r power of the engine i8 needed. A greater specifi~ lo~d on the propeller during the t~ke-off bring~
about greater velocltles of the air flow under e~id pro peller ~nd a profound ero~ive e~ot of the jet on the `
80il. Although this effect i~ ~m~ller th~n th~t of the ..
mschine with ~ertichl t~ke-of~ ~nd lAnding, whloh util~
ze~ ~ reactive ~et, a~ 3et forth in the ~RD patent No.
10 1246422, Cl. B 60 V 3/0~, it ~a ~till ~ery hleh for the , maJority o~. 80il ~ites. ~he machlne generate~ a ~trong aoouytic field. Be~idee, the pree~noe of ~aid tilting .
wl~ with a propeller group make~ the dea~&n o~ the machi-ne more compliosted ~nd reduces it~ rel~abllity in gene- j~;
ral. A tr~neition o~ the m~ohin~ from the tak~-off oondit-lona lnto those of the level fli~ht and back i~ ~ery com-plicated ~or the control ~y~tem~ Any aooidental ~ailure in the control ays~em ~nd in the mechRni~m o~ the outer win~
psnel tilting m~y re~ult in a grave damage.
~own are comblned flying machine3 with ~ticsl ~
t~ke-e~f ~nd l~ndin~ in whlch the liftin~ rotor 18 ~rr~n-ged ineide the fu~el~ge of the m~chine. In said flyin~ ma-chine, protected by the U~SR In~ent~r'~ Certiflo~te No~
1550790, Cl. ~ 64 ~ 1/00 of 1987, the fu~el~ge ia made up 25 in the ~h~pe cf ~ aymmetrically cambered di~k (toru~),to which co~nected a~e wlne~, ~ t~il unit ~nd ~ cabin. In the center of the di~k t~ere is a vertic~l tunnel th~t - :
house~ ~ oentr~l body ~nd a li~ting rotor. ~he inlet ~nd outlet ~Qotio~s of aaid tunnel are closed wit~ turn~ble shutters, whlch ~re closed under the condition~ o~ ths leYel flight, ~ormin~ ~ smooth upper ~urface of s~ld disk.
Under the t~ke-off condltion~ the turn~ble shutter~ on the upper ~ur~ce o~ the di3k turn ~ertic~lly, opening ~n ~ir aco~ into th~ ve~tio~l tunnel- An inlet ~lr int~ke opening.o~ ~id vertic~l tunnel is ~ormed by oh~nnels between turnable ~huttexa. An ~nnul~r v~lume of ~ald disk ~a filled up with B light ~8, ~r~hich creates an ~ero~t~-~i :: :

~1~8797 ~

tic lift foxce. The machine i8 pro~lded with propul~ion .
propell~r~ on the wlnga for the conditlons oi the level fllght ~nd with a landing gear on ~ir cu~hions. The av~ f abillty o~ ~olume~ lled up with ~n l$ght gaa, makes 5 lt pos~ibla to reduoe the li~t force of the propeller and thereby to reduce t.he power of the engine. C~lculation~
hhvs ~hown that the ~ero~tstic lift ~o~ce hs~ an e~3ent~
effect on the value o~ th~ r0quired liit force of' the ro~
to~ t~e tunnel only i~ caas the overall dimen~ion3 ~nd 10 load-lifting c~pacity of the maohine are ~ubatantisl .
(wlth the di~m~tex of the disk exceedlng 50 m)~ Por ~lyl~g machlnes hsving a tske-oif weight les~ th~n 50 t Q 6~1n in the l~t force of the propeller turn~ to be lnaignifio~nt.
~ald machi~e i8 provided with turnable ~h~tter~ on the 15 uppar sux~ace o~ the diak, which ~e opened under the co~-dition~ Or tske-of~ ~nd l~ndlng. These shutter~ displ~y ~ great ~erodynsmio drag in the incoming ~ir ilow, which i9 e~eci~lly notic~ble under the trsnsfer cond~tion3, ~ince e~en with minor opening o~ s~ld s~utters the Qero-20 dyn~mic dr~ of the flying m~chine sh~rply ri~e~ ~ Durlng . .
B tr~nalt~on *rom the level fli~ht to l~ndin~ the flying ~chine msy lo~e it~ ~tability be~ore the lifting rotor h~
a~ opportunity to stQrt apinning. Said machine fe~ture~ low serodyn~m~c characteristi¢s, becau~e under the acceler~tion .
25 cond$t~0n8 the di3k rem~in~ horizont~l ~nd does not d~ve- ; :.:
lope a lift force, the whole o~ the lift force i~ built : :
up by thc wingo. Vnhen takin3 lnto consideration the oYer ~11 dimen~lon~ o~ the di8k ~the dlQmeter in axcess Or 50 m), ;~:~
one como~ to ~ ¢onclu~ion, thst the ~reater part of the 30 3urf~ce of the ~lyin~ m~Ghine doe~ not tQke part i~ deve- :- :
loping the serody~mlc lift force. : ~-Tha cio3~t to the ~pplied ~n~ntion in it~ tso~nlcal ;~
e~3e~ce i~ ~ fly~ng m~ch~ne acoording to the Gre~t Brit~in ~stent No. 1331655, Cl. 3 7 W of 1973. Said ~lying m~ohin~
35 comprlses ~ fu~ela~e, manuf~ctured in the ~h~pe of a thick l~tin~ wing h~ving a ~orm of a diak with ~ ttened bot- :~
tom~surface ~nd sn ~ymme~io~l cro~s-~ction. ~he ~usel~
....
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~ 21~7~7 ~ ~

ge ia furni~hed with a o~mbered tunnel with inlet ~nd out- :
let opening~ in Y~hich there i~ horizontslly mounted lift-in~ rotor. ~he bottom ~ur~ace of the ~usel~ge mounts ~ , l~ndin~ de~lcs on an air cu~hion, whioh surround~ th~ out-let from the tunnel. S~ld machine i9 provlded with out- ..
board wing~ and twin-fin tail unit. For the level Slight t,~e flyi~g machine i8 equipped with propul~ion pro~ellers and a ~et nozzl~. ~ho l~ftine rotor ~nd the propul~ion ` prop~llers are brought into rotation from ~ common power , 10 pl~nt. S~id flying ~achlne i~ equlpped with ~n open ~ir l~take that face~ the incoming air flow a~d i~ di~po~ed on the uppe~ sur~ce of the central wing, ~upplying ~lr into said tunnel. Ihe elr int~ke~ of the power pl~nt are arranzed behind the ~ir int~ke of ~id t~nel ~nd are sh~-15 dowed by s~id.elr ~nt~ke. , A dr~wb~ck of sAid flyin~ maohine i~ en incres~ed ~erodyn~mio dra~ ~n the le~el flight, which is ceuaed by the pre~enae of ~ pe~m~nently oper~-ting olr intake o~ the tunnel. In the ~roce~s, said increa~ed aerodynamic dr~g 20 i~ connected not only with the pro~ectlon of th0~ir inta-ke into the lncoming ai~ ~low, but sl~o with ~ drop of the ~ir, bled from the upper surfaoe, practlc~lly perpendlcu-lar to the bottom eurface of the fu~el~e, whleh al~o crea-te an ~dditionsl re~i~tance to tha incoming ~low. Like in all other flying machine~ with vert~cal take-off snd land-inB of thi~ type it does not link th~ ch~r~oteriatic~ of the lifting rotor and the l~nd~n~ devioe on the ~ir cu~hi-o~, which turns them into a ~imple ~ggreg~te of the prior ~rt deYlce~ (ag~reg~tion).
Dl~clo~ure o~ the Invention T~e purpo~e of the pressnt in~nt~ on ia a cxeation of ~ combin~d ~lying m~chi~e, in which ~ propell~r ~nd a l~n-d~ng device fe~ture an opti~l coord~nstion. A further pur-po9e of the l~ve~tion la ~ improvem~nt of the aerodyn~mic charsctari~tic~ of the flyin~ ~achine in the level flight.
A ~till ~nother purpo~e of the invsntion ~g ~n lm~rovement . .

` ~14g797 - 6 ~
of t~e ~irflow ~round the ~lying machine ~uselage by the incoming eirflow. An ~uxiliary purpo~e of ths lnvention i~
an increase in the op~xation reli~bility of the combined fly~ng m~chine, with a reduced power of the power plant during landing lncluded.
To att~in the enumerated ~bove purpo~e~, the combined ilying m~ohine, compri~ing B ~u~el~ge, m~nuf~ctllred in th~
eh~pe o~ a t~ick centre,l w~g wlth ~ 6~ymmetrical cro09-section~l profile having a vertical tunnel th~t hou~es ~ , llftin~ rotor, ~nd outboard wing~ ~nd ~ tail unit, pro- .
, , pul~ion prop.ellers ~or the level fli~ht, a power pl~nt for dr~ing propul~lon and liftin~ propeller~ ~nd a land-lng d~lce on an air cu~hion? ~urrounding ~n outlet from eGid tunnel, ~c¢ordin~ to the lnvention, i8 provided wi~h ~
15 ~ ~y~tem of o~angin~ the common ~nd cyclio ~tep of the ~ :
li~ting rotor, with nn inlet opening of ~aid tunnel being 5~
formed by a toru~ ~urface, conjugated with the upper ~ux- .
face o~ the central Y~ng, with the cros~-~ectional srea :.
of the ~ertical tunnel ln the pl~ne of the lifting rotor rote.tion being 0.3 to 0,~ of the area OI the la~ ine devi- i ce ~ r ¢u~hlon. ' ~ :
!rhi~ being the c~e, the powex pl 3nt ia m~de up OI ~ . :
two a~ e modul e~, ~rranged in bhe o ~ntral win~ *rom two ~: :
side~ of the vert~oal tunnel, ~nd h~ two propulalon pro-~ ~
~5 peller~, with the li~ting rotor being conneoted to the ~-both engine modulea, whiie e~ch of the propul~ion propel-- ::
ler~ i~ connected to it~ ow~ en~3;ine module . - :::
E'urthermor0, th~ propul~ion propellers ~or the lev~1 . :
fllght ~re mounted ~bove the upper sur~oe of the ste~n p~rt oî the centre.l wing beyond the line of the m~uclmum t~icknos3 of the centrsl wi~g ~tern part profile.
In thi~ ca~e the propul~ion propeller~ are mounted on pilona, disposed from two side~ rel~tive to the tunnel.
3e~-ides th~ flyi~g machine i~ provided with two lon- .
gitudinal be~ms, extending ~bove the up~er s~face of the : -stern p~rt Or the centre.l wlng ~d be~ ng di~posed from two cidea relE~ti~re to the t~el, ~ith the tail unit being ~ . -.
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.. .. ' ' . ', . ~' . . . , ,, , , , . ~ ,,, . ~ ,, . . " . . ' ', 21~8797 ~
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~ade up in the sh~pe of two ~in~, f~tened on the longitu-dinal be~ma, ~nd ~ hori~ontal ~tsbilizer of the t8il unit th~t cro~ses said fin~, w~ile the propul~ion propellers .
~re arr~n~ed in front of the fins.
~he esse~ce of the inve~tion ~nvolves the inclusio~
of the ~rertic~l tu~el with the lifting ~otor into the ~e-rodynamic arrengement of the combined flying machine under the level fllght conditions and, in the proce~, the pro-~ on ~or ~ aBrsement between the characteristic3 of the air cu3hion and the lifting rotor, whlch will impro-ve the se,fety of ~light and the aerodyn~mic ch~r~cter- :
istics of the machine, ~nd specific~lly will r~i~e it~ .
serodyn~m~c e~ficlency. ~he manufacture of the ~lying machlne fuselage in ~ ~ape of ~ thick central wing r~th ~n 88ymmetrical cros~-seotional pro~lle, having ~ ~ertic~l tunnel with open inlet ~nd outlet opening~, in which s~id inlet opening i~ formed by a torus surface, ~moothly con-ju~ted wl~h the upper surf~ce of the central wing, ensu-rl~ ~ flo~-over o~ the centr~l wing in the tunnel zone as 20 O~ two sequen~lally mounted ~erodyn~mic profiles, ~imil8r-ly to a fl~t ~nnular wing. In thi~ c~e the s~adow~ng of the tunnel by the lifting rotor constitutes no ob~t~cle to ~etting up t~e ~low~over condit~on~, like in the ~nnul~r wing, which ensureu positive ~erodynamic chacarat~ri~tics 25 of the flyi~g maohine. The reduction of ~hado~n~ o~ the tunnel by the lifting rotor i~ a~isted by the ~election : ~i o~ the tunncl cro~s-~ection~l area in th~ plane of the ting rotor rotBtiOn ~t a level of 0.3 to 0.8 o~ the area of the landing de~ica sir cu~hion, where~ the a~ilabllit~
30 Of the ~y~tem for ch~nging the common ~nd cyclic pitch o~
the llfting rotor with the r~tio of areas selected, pro~i-~e~ for B rell~ble tr~n~ition f~om one regime to ~notherdurine the fli~ht. At take-o~f when oper~tin~ in the re-~lme of the air cushion, the li~ting rotor fe~tures the 35 mlnimum step and the minimum loading on the ~wept area.An increQse in the altltude of fli~ht du~in~ t~ke-off i9 achieved by a change in the co~mon ~tep of the llfting ro-21~797 to~ during the transition of the flying mi3chine from the re~i me of the Bir cu~hlon into thiB hover regime over the screen with the control of the flyine m~chine attitude by means of thi3 system for changing the common and cycllc ~
5 pitch of the li~ting rotor. In t~e proce3~ the rpm of i ~ ,, the power plant are not practlc~lly ch~nged, and ths power plant operate~ on the r~ted revolution~ with a h~gh eifi-ciency. At the area ratios selected, thi3 air cushion pro-vide~ ~1BO ~or d~mping accidentQl VBriatlOns in pres~ure 10 within the tunnel behind the propeller, which increa~e~ ; .
the sti3bility of the li~ting.propeller oper~tion ~nd tha :
oper~tion of the flying machine in gener~l. ~.
~he disposition of the propulsion propellers above , the upper ~urf~ce o~ the stern part of the oentral wing beyond the line o~ the m~ximum thiokness ~lues o~ the ~erodynamic pxofile f~ours the flow around the fueelQ~e in t~e re~me o~ ~he ~nnu~ar wing, ~ince the propellers in- ni tensify the ~irrlow of the upper ~ur~ace of the stern part ~ :
of the wing, ~oreover, in c~se the propul~ion propeller~ ~ :
~re di~posed with a displacement from two ~ides rel~ti~e to the tunnel, the propulsion ~opellers ~nd the lifting rotor have a minimum effect on each other. `L`^
2he impl~menting o~ the power pl~nt in the *orm o~ ;
tY o engine modules, arranged in the fusel~ge from two ~i-25 des rel2tive to the tunnel, makes :lt~ longitudin~Ll balano-ing simpler~ since the engines s,re po3itioned close~ to t~e lift ~ppllc~tion point of the rotor in the tunnel, and are mounted symmetrically ~bout the longitudinnl ~x~
of t~e m~chine. The connection of two engine modules to 30 the li~tine rotor ~nd by OnQ to each of the propulsion . . :
propellers incre~se~ t~e reliability of the flying mschi- ~::
ne, ~g ~ f~ilur~ of one of the engine~ doe~ not result in -the lo~ o~ all the power a~ailable. As ~pplied to the pre- ¦
eent invention, ~n ~dvantage re~ides in the ~act th~t with 35 the selected relation of the ar~s o~ the tunnel in the : ;
pl~ne of the rotor rot~tion and o~ th~ air cu~hion o~ the l~nding devi¢e, one engine module is suf~icient to land .~_ .

~,'','..'''.'..','"'.`;'','',''; . ' ' ' ';

~ 214~797 _ 9 _ s~ld flying ~achine, since the transition from the level flight to ho~e~lng over the landing ~ite i~ possible in the hover regime over the soreen, thst i~, st B sufficie~t al-titude to h~ve time ~or the 6elect:Lon of ~ site for lAnd-ing ~nd for mov~ng toward~ it in the ~light re~ime overthe ~creen or on the air cus~ion, for whlch purpo~s the power of one engine module i3 adequate~
!Ihe longitudine.l be~ms, which proJect ~bove the upper ~urface of the stern p~rt, improve its aerodyn~mica by 10 reducing overflow along the late~al edge o~ the centrQl :
wing. In thc proce~s, the fins ~nd the hor~zontal ~t~bili-zer are t~en out of its aerodynamic shadow. The di~posit- .
lon of the propul~ion engin~ in front of the ~in~ improve the controllabill~y of the flying machine at low speed~ o~ ;
15 flight.
The Applic~nt 18 not in the know of any combined ~lying machine~ ~3~ing the applied combination of ~e~tures, which confirm~ the compli~nce of the in~entlon to the , "no~elty~ oriterion. The ~pplied combination o~ essential :
~e~ture~ i~ not readily apparent from the prior ~rt and, consequently~ ~aid invention meeta the "inventive le~el" .
requirement, . ;
~rie~ De3cription of the Dx~wings ;
~he invention i~ explained wit~ the aid of dr~wing~. . .
~igo 1~ General arr~ngeme~t of the flying m~chine -top ~iew w~th the ~Xi~ of the fuselage upper ~uxface p~rt-ially removed. .
~ig~ 2~ ~ongitudinsl cro~s-section of the flying ma-chine ~long line A-A. . :~
~igs 3 and 4 . System for changing the common ~nd cyc-lic step of the lifting rotor. Axonometry and general diagram.
. 5. ~ront ~iew of t~e flyine m~chine with propul-~ion propellers, disposed in front o~ the fln~.
Fig3 6 ~nd 7. Side ~nd front ~iews o~ the ~lying m~
chine with propulsion propellers dl3posed on pilon~.

~` 21~8797 ~ ~
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Preferred Embodiment of the Invention ~ ~ :
Said combined flying m~chine comprisea ~ fusel~ge 1, , m~u~ctured ln ~he form of ~ cent.r~l wing ~ thick ~ymme- ~ .
tric~l cro~3-section with ~ cambered in plan le~dlng ed~e 5 ~nd a ~traightllne trailing edge, smooth l~teral outline~ :
~nd a fl~ttened bottom ~urface. ~h3 fusel~ge i9 provided with B vertlc~l tunnel 2, h~ving a rounded inlet edge. :
Said tunnel of an ~nnular cros~-eeotion occupies the m~in ~r~s in pl~n in the central part of the fuselAge. Inoide s~id tunnel there i9 a 3treamlin~d centr~l body 3 with lifting rotor 4. Sald central body is connected with the tunnel w~ll by r~di~l pilons 5. ~h~ flying maohine i~ equipped with B c~bin 6 to house the c~ew, pa~s~nger~
~nd lo~ds, outboard wing3 7 and ~ t~il unit 8. ~he ~ero- .
15 dynamdc ~urf~ces o~ ~id ~lyin~ ~achine - the outboard ; ~
wing~ and the tail unit, ~re provided with defleotable ~; :
control elementc, for in~t~nce, with ~l~ps 9 ~nd 10 and : t,4 , . :
rudder~ or the level flight the flyin~ machine ls ~
furnis~cd with two propulsion propeller~ 12- The liftlng S . .
20 rotor 4 Bnd the propul~ion propellera 12 ~re brought into rot~tion by a power pl~nt th~t includes tY~o engine modu- .
le8 13. ~he engine modules 13 are arr~nged in the ~u3ela- :~
ge 1 from two side~ rel~ti~e to the tunnel 2. Said engine modules are connected by 9~f~3 14 wlth the l~fting rotor . .
2S and by sh~fts 15 with t~e propulsion propellers. Both en- .
gine modules ~re connected with the liftin~ rotor, whcre-each of th~ propulsion propeller~ io oonnected with it~
own engins module. ~h~ shaits 14 are connected ~t one side to the reducticn gear 16 of the li~ting rotor, snd at the ~ -other slde to 8 cont~oll~ble coupling 17 on the engine module~. 3~id controll~ble couplin~s 17 m~y be o~ ~ny o~ l -the ~ollowing type~s hydraulic, mechanical, electromagne-tic. Ths ~h8ft 15 i8 con~ected with the engine module by means o~ ~ oontrollable coupling 18, pre~er~bly with an ¦
~dju~t~ble ge~ring r~tio. S~id coupling~ 18 ~ay be of any type. ~e ~lyin~ machine is equipped with a l~nding de--- 21487~7 -- 11 -- ~
~lce on an air cu~hlon 19l surrounding ths outlet out o~
the verticsl tunnel. The area of t~e tunnel cro~s-~ection in the plane of the lifting rotor rotat~on amount~ to 0.3 to 0.8 from the arear of the air cu~hion of the l~nd-5 ~ ing device 1~. Speol~ically, in ~ ~lying maohine with a capacity of 18 peopl~ the area of the landin~ device air .
cu~hlon ~mou~t3 to 58 ~q. m, while the area o~ the ver-tical tunnel cro~-section i9 38 ~q. m in the plane of the lifting rotor rotation. The inlet opening of the ;
tu~nel i~ *o~ned by a torus ~urf~ce 20, smoothly coniug-sted with the upper aur~aoe of the centr~1 wing. As a result, in the middle part o~ the central wi~g thsre Are thick ~erodynamic profiles, made up in succes~ion, ~tre-~lined under condition~ simil~r to an annular wing, which improves the ~erodyn~mic c~aracteriatic~ of the flying m~chine ln the level fli~ht.
The ~lying machine is provided with a sy~tem to .
chenge the ¢ommon ~nd oyclic step of the lifting rotor.
~he bl~des 21 of the li~ting rotor ara hinged to the oen-tral cross-piece 22, secured to the output ~hs~t 23 of the reduct~on gear 16. ~he msin unit ln the sy~tem of ch~n~-ing the oommon and cyclic step of the lifting rotor i9 ~
~washpl~te, compri~ing a rot~ting r~ng 24, non-rotating .
ring 25, torque-~rm~ 26 and a card~nic ~UspenSiOR 27. The rotating rinB 24 i~ connected by means of CQrriers 2B
wi~h the blade8 21 o~ the lifting rotor. The non-rot3ting ring and the card~nic su~pen~ion 27 ars connected by pull rod~ 29 wit~ t~e levers, controllin~ the common ~tep o~ 1 :
the lifting ~otor 30 ~nd the cyclic ~tep o~ the li~ting rotor 31.
Th9 propulsion propellers Are mounted ~boYe the up- : ~:~
per surf~oe o~ the centr~l wing gtern pQrt beyond t~e li- .
ne of the m~ximum thick~ess profile o~ the central w~ng :~
stern part, coincidi~g with the inlet edge of the tunnel to~u~ inlet opening. ~he ~peoi~ic ~one of the pro~ulsion propel~ers arrangemont i9 determined by wind ~unnel test8.
In p~rticul~r, ~he propul~ion propeller3 ~re di~posed , 48797 ~

with ~ misalignment toward~ the trailing edge o~ the cen-t-r~l wing. Depending on the o~rall dimen~ion~ and the load-c~rrying c~pacity of the ~lyi.ng m~c~ine, the propul-~ion propeller~ are dispo~ed either on pilons 32, or on the tail unit. me pilons 32 are ~rrsnged from two ide3 relati~e to the tunnel 2.
A flying machine with propul ion propeller~ on the tail unit are pro~ided with two longitudinal be~ms 33, .
proJecting above the upper surf~ce of the stern part of the middle wing, two fins 34 ~nd a horizontal st~bili2er 35 ~h~t cro~ses the fin~. The propul~ion propeller3 are mounted ln front of the fin~ 34.
Air int~kes 36 of the power plant are di~po~ed on the upper ~urfaoe o~ the centr~l win~- i~
1~ During ~ take-o~, the blades 21 of the li~ting ro- : .
tor 4 sre set to the po~ition of the minimum ~tep ~nd the power plant i~ ~tarted with the shafts 15 o~ the pro- :
pulsion propellers 12 drive disengeged. The li~ting rotDr 4 i~ ~pinned up and air i9 forced into the cavity o~ the l~nding device on the ~ir cu~hion 19. Using the common step control leYer 30, pre~sure in the air cu~hion i~ in-cre~ed until the ~lyi~ machine lifts off from the t~ke- .~
of~ sito. A~terw~rds the common ~tep of the lifting ~otor .~ -i8 incxe~sed ~nd the flying m3chine is tr~ngferred into the condition~ o~ hover over the screen. ~he flying m~-chine i~ controlled in the hover re~ime by me~no o~ the lever 31 controlling the cyclic etep of the lifting rotor and the ~wa8hplate of the ~y~tein c~snging the common and .
cyclic step of the rotor. With ~ further increase of the common atep the lift ~orce o~ the lifting rotor 4 becomes oqu~l or ~reater than the weight of the flying m~chine, I ~nd the latter i~ tr~nsferred into the conditions of sus-; tainin~ in the ~r ~t ~he 3~crifice o~ the liftin~ rotor~. ~or the accelerstion o~ the ~lying m~chine the coupl-in~ 18 io eng~ged and the propul~ion propeller~ ~tsrt~pinning up. The thru~, developed by the propul~ion pro-pellers builds up ~radually snd at the initial st~ge of aoceler~tion thexe ie no need o~ con~ider~ble expenditure ., ,.. . . . ... . ... ~ .. . . .. , . .. .. , ~ ... .. . .

~ 21~8797 of power to drive the propul~ion propellex~. ~lncs the centr~l wing h~ an a~ymmetrical cros~-~ection, ~ lift force ~t it i~ developed during ~ displacement from the zero angle o~ ~tt~ck. An additional lift ~oxce ~ inducsd by th~ outboard win6~, ~hich a~e ~et ~t the optimum ~ngle of Qttack. With ~n increa~e o~ the ~peed of flight, the aerodynamic lift ~orce rise~ ~nd, rQspecti~ely, the lift ~orce ~t the rotor 4 i~ reduced by ~ change in its common ~tep. ~he ~a~ed powar of the power pl~nt ~a trans~erred to the propul~ion p~opellers t2. On obt~ining the aerody-n~mic lift rorce ~alue equal to the wel~ht o~ the flying machin~, the liftin~ rotor 4 iB di~e~aged from the power pl~nt ~nd the ~lying m~chine proceeds flying in ~ocordan-ce with th~ ~irpl~ne arrangement. l`he tr~nsitlon to flight ~ccording to the ~irplane ~rr~n~ement does not require the cloaing of the inlet opening of the tunnel, : ~ ~ :
~nd thorefore the di~eng~ement o~ the lifting rotor 4 .
does not cau~c ~ change ~n the ~erodyn~mic dra~ of the flying machine, which makes the control of the flyin~ ma-20 chine simpler ~nd ~ncreaees it~ reliability. ~he flying : ::
m~chlne i9 kept in the ~ir due to ~ lirt, induced by the . :~
tot~l 3urf~ce - the ¢entral wing ~nd outbo~rd wing~, . ~: :
which improves t~e serodyn~m$c coef~icient o~ the m~chine.
S~id ~lying mschine ha~ no ai~ intake de~ice o~ the tunnel that projects lnto ~he incomin~ ~low o~ air, which redu-cee its aerodyn~mic dr~g and impro~es the ~ero~ynamic ef- ::~
ficiency o~ the flying machine. When flyin~ at a rated speed, the li~t~ ng rotor doe~ not ope~ate and ~ir freely flows through the tunnel 2, flowine p~t t}~e leRdlng edge :.
30 and trai~in~ ed~e part~ of the wing under the conditions ~imil~r to the ~low over the flat snnular Y~ng.
' During land$ng t~e horizo~tal ~peed of ~l~g~t i~ redu-oed ~nd wlth a arOp 0~ the aerodynamic lift force down to ~ Ue less th~n the weight of the ~lying machine, the :~
coupling 17 is engaged and thc liftin~ rotor 4 is spi~led up at a minimum common step. The power plant hs~ ~n exce~s Or power and the ~pinning up of the li~tin~ ~otor will ';,..
. .'.'.''~
: :.'.

` ~148797 . - 14 -not c~u~e a decxease in t~e horizont~l thrust of the pro-pulsion propeller~ 12. The spinning up o~ the lifting ro- .
tor will not cause either ~ ~ubstanti~l ch~nge in the ~ero-dyn~mic drag of the flying mQchine, since there i9 not ns-5 ce~sity to open the inlet opening of the tunnel. W$th a .
decre~e o~ the horizontal ~peed of ~light more power i8 .
tran~ferred to ~e lifting rotor, and the flying machine i9 placed ~nto the ho~er regime due to the lifting ~orce:~
of the rotor 4. ~hen a vertical landing of the *lylng m~-ohine i9 carried out on ~ site ~elected. If required, the ~lying machine hoYer~ o~er the eround surface or over w~- :
ter Rnd i~ mo~ed tow~rds the place o~ l2ndin~, or in the .
~light regime over the ~creen, or on the ~ir ouehion.
Takine into consideration the f~ct that the power .
required ~or hovcring o~ the applied flying m~chine over the screen amount~ to les~ than the total power of the :
power pl~nt, ~sid flying machine can, if required, mske a landing u~ing one engine module 13. ~hi~ being the oaae, the fly~n~ mao~ine de~cent~ down to ~n ~ltitude at which 20 the sc~een e~ect appe~r~ and tran~fers from the horizon- :
tal flight according to the airplane ~rr~ngement to the hover regime o~er the ~creen. U~ing ~ simila~ procedure it is po~sible to t~ke-o~f the flying mQchine in emergen- : ~:cy. ,~ :~
Indu~tri~l Applioability ~ he po3~ibility to realize ~id flying m~chi~e acco~d-ing to the invention i~ confirmed by the tri~l o~ a model s~mple of the ~pplied flying m~chine~ A ~ull-3c~le flyin6 m~chine mgy be manuf~ctured, uQ~ng modern tach~ology ~nd mPterial~ of the a~iation indust~y.

Claims

Claims:

1. A combined flying machine, comprising a fuselage (1), manufactured in the shape of a thick central wing with an asymmetrical profile, having a tunnel (2) with open in-let and outlet openings, in which there is arranged a lif-ting rotor (4), outboard wings (7) and a tail unit (8), propulsion propellers (12), a power plant for driving the propulsion propellers and the lifting rotor, and a land-ing device on an air cushion (19) that surrounds the out-let out of the tunnel, c h a r c c t e r i z e d in that it is provided with a system of changing the common and cyclic step of blades (21) of the lifting rotor with the area of the tunnel cross-section in the plane of the lifting rotor rotation amounting to 0.3 - 0.8 of the area of the landing device air cushion, in this case the inlet opening of the tunnel is formed by a torus surface (20), conjugated with the upper surface of the central wing.

2. A combined flying machine according to Claim 1, c h a r a c t e r i z e d in that the power plant is made up in the form of two engine modules (13), disposed from two sides relative to the tunnel (2), and it is provided with two propulsion propellers (12), with the lifting ro-tor (4) being connected to the both engine modules, where-as each of the propulsion propellers (12) is connected to its own engine module.

3. A combined flying machine according to Claims 1 and 2, c h a r a c t e r i z e d in that the propulsion propellers (12) are mounted above the upper surface of the stern part of the central wine beyond the line of the maximum thickness profile of the stern part of the central wing.

4. A combined flying machine according to Claims 1-3, c h a r a c t e r i z e d in that the propulsion propel-lers are mounted on pilons (32), disposed from two sides relative to the tunnel.

5. A combined flying machine according to Claims 1-3 c h a r a c t e r i z e d in that it is provided with two longitudinal means (33), projecting above the upper surface of the stern part of the central wing and dispo-sed from two sides relative to the tunnel, with the tail unit (8) being made up in the form of two fins (34), mounted on the longitudinal beams, and a horizontal stabi-lizer (35), crossing said fins, whereas the propulsion propellers (12) are disposed in front of the fins.